The throat and exit areas of a convergent divergent nozzle in a wind tunnel are 4 cm2 and 10 cm? respectively. The reservoir conditions are 10 bar and 95 °C. Find out the Mach number, pressure and temperature of the air at the test (exit) section. Also, find the mass flow rate.

The throat and exit areas of a convergent divergent nozzle in a wind tunnel are 4 cm2 and 10 cm? respectively. The reservoir conditions are 10 bar and 95 °C. Find out the Mach number, pressure and temperature of the air at the test (exit) section. Also, find the mass flow rate.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Related questions

Q: Air at 800 kPa and 1200 K enters a converging nozzle with negligible velocity (i.e., these are…

Q: ir, at stagnation conditions of 450 K and 250 kPa, flows through a nozzle. At section 1, where the…

Q: An aircraft with nose M1 P1 T1 properties of the upstream unifrom air M2 angle 0 = 15° as shown in…

A: nose angle θ = 15° Mach no M1 = 2.5 Upstream air pressure = P1= 60 kPa Upstream temperature = T1 =…

Q: What would you have to do to reduce this flow angle to zero degrees?

A: Here the reducing flow by zero degree angle attack

Q: Q3. A supersonic flow of air has a pressure of 1 x 105 N/m2 and My a temperature of 350 K. After…

A: given data;⇒pressure(P)=1*105N/m2⇒temperature(T)=350K⇒mack number(M)=3.5

Q: Design the 2D steady MOC contour for a super sonic nozzle assuming that the expansion section is a…

A: To design the 2D steady Method of Characteristics (MOC) contour for a supersonic nozzle, we need to…

Q: 3. The NASA X-43 flies at a Mach number of 9.4 at an altitude of 30,000 m, where thepressure is…

A: a. V=2832.61sm,T0=4219.872K,P0=32962kPab. vs=1303.87m/s, T0s=77941K, P0s=3392510kPac.…

Q: Nozzle is assuming steady one-dimensional flow. M = 2.731. This is the the supersonic flow of air…

A: To calculate the mass flow rate of air through the nozzle, we can use the continuity equation, which…

Q: equal to 3.0. Find Me, Pe, and the loss in stagnation pressure (Poi - Poe). Repeat for a ock at the…

A: Given Image,

Q: When operating at design conditions (smooth exit to sealevelpressure), a rocket engine has a thrust…

A: Write the given data.

Q: What is the area where the shock appears? Calculate (b) the pressure and (c) the temperature…

A: Given DataThe reservoir temperature of air T0= 350KThe reservoir pressure of air P0= 500 KP aThe…

Q: 1) What is the value of static temperature, stagnation temperature and stagnation pressure in the…

A: To calculatethe static temperature, stagnation temperature and stagnation pressure in the test…

Q: At a certain point in a pipe, air flows steadily with a velocity of 150 m/s and has a static…

A: DISCLAIMER FOR MULTIPLE Since you have asked multiple questions, we will solve the first question…

Q: 1. Air, with stagnation conditions of 800 kPa and 100 °C, ex pands isentropically to a section of a…

Q: The Pitot tube on a supersonic aircraft (see the Video) cruising at an altitude of 25000 ft senses a…

Q: Air flows through a duct as in Fig, where A1 =24 cm2, A2 = 18 cm2, and A3 = 32 cm2. A normalshock…

A: Given: Mach number at section 1,Ma1=2.5 The pressure at section 1,p1=40 kPa The temperature at…

Q: Air flows through a constant-area, insulated duct. At location 1, the conditions are Maj = 0.4, T; =…

A: Given: The mach number at location 1, Ma1 = 0.4 The mach number at location 2, Ma2 = 0.8 The…

Q: est section. Find the temperature and pressure in the test section and the upstream K kPa K

A: The mach number given as .The velocity given as .The density given as .

Question

The throat and exit areas of a convergent divergent nozzle in a wind tunnel are 4 cm2
and 10 cm? respectively. The reservoir conditions are 10 bar and 95 °C. Find out the
Mach number, pressure and temperature of the air at the test (exit) section. Also, find
the mass flow rate.

Expert Solution

This question has been solved!

Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.

This is a popular solution!

SEE SOLUTION Check out a sample Q&A here

Step 1 Given Data

VIEW

Step 2 Calculation

VIEW

Step 3 Calculation

VIEW

Trending now

This is a popular solution!

Step by step

Solved in 3 steps with 3 images

SEE SOLUTION Check out a sample Q&A here

Knowledge Booster

Learn more about

Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.

Similar questions

A uniform supersonic flow of air at Mach 3.8, with a stagnation pressure of 5.0 MPa and stagnationtemperature of 1100 K, expands around a 23o convex corner. Determine the downstream Mach
Q2: Air flows isentropically through converging nozzle which has a throat of 7 cm?. The stagnation conditions are 130 kpa and 380 K. Find the exit pressure and mass flow rate if the atmospheric pressure is: (a) 88 kpa. (b) 40 kpa. (Take: K = 1.4, C, =1005 J/kg.k and R = 287 J/kg.k for air)
(Q) A converging-diverging nozzle discharges an over-expanded jet into a room. Calculate the deflection angle in degrees caused by the oblique shock forming at the nozzle exit? Ratio between the room pressure and the pressure at the nozzle exit is 5.4. Mach number at the nozzle exit is 1.5. Assume the fluid to be air as a perfect gas with k=1.4
2. The total temperature and total pressure (absolute) in the reservoir of a converging-diverging high-speed wind tunnel are 500K and 3x10 Pa, respectively. The throat area is 25 cm² and the Mach number in the test section is 3.0. Find the test section area in cm2, mass flowrate in kg/s, pressure in Pa, temperature in K, and air speed in m/s in the test section.
Air flows steadily from a tank through the pipe inFig. . There is a converging nozzle on the end. Ifthe mass flow is 3 kg/s and the nozzle is choked, estimate(a) the Mach number at section 1 and (b) the pressureinside the tank.
A turbojet engine with a convergent divergent nozzle expands the flow such that Po = 0.8 P, The engine has the following data at a flight Mach number of 1.5 : Te = 7.5 ,Tt4=1400 K, e. = et = 0.9 , y = 1.34 ,CP; = 1135 J/kg.K If the jet velocity is 1025 m/s, determine the flight altitude.
Gas dynamics
Please Help with this question. Show clear steps and highlight the answers. Also explain the sub question related to the main question please. THanks!
Consider steady, isentropic flow of air through a duct with varying area. At section 1, p1 = 60.0 kPa (abs), T1 = 27°C, Vị = 486 m/s. At a downstream section 2, p2 = 78.8 kPa (abs). Determine: a. Mach number, Maz b. sketch geometry of the duct
The velocity ratio(v1/v2)of an isentropic flow through a supersonic wind tunnel is 0.915 ifthe velocity and mach number at the exit are 376.95 m/s and 2.60 respectively find the value of speed of sound at the entrance